EP0950859B1 - Gasabscheider für eine Brennkammer mit zwei Brennerköpfen - Google Patents

Gasabscheider für eine Brennkammer mit zwei Brennerköpfen Download PDF

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Publication number
EP0950859B1
EP0950859B1 EP99400918A EP99400918A EP0950859B1 EP 0950859 B1 EP0950859 B1 EP 0950859B1 EP 99400918 A EP99400918 A EP 99400918A EP 99400918 A EP99400918 A EP 99400918A EP 0950859 B1 EP0950859 B1 EP 0950859B1
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EP
European Patent Office
Prior art keywords
tiles
sectors
walls
combustion chamber
heads
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP99400918A
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English (en)
French (fr)
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EP0950859A1 (de
Inventor
Alexandre Forestier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP0950859A1 publication Critical patent/EP0950859A1/de
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Anticipated expiration legal-status Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

Definitions

  • the two heads are delimited in the chamber end, by a ring called separator and thus form two concentric ferrules.
  • This separator is a critical element in the design of the room because it is subjected to longitudinal stresses and tangential during operation of the chamber.
  • the separator ring is consisting of a plurality of sectors arranged circumferentially at some distance from each other.
  • Such a ring is disclosed in document EP-A-564170.
  • the external walls of the separator are subject to very high temperatures, moreover, intersections of these separators are favorable for recirculation hot gases between the two heads.
  • the object of the invention is to thermally protect the outer walls of the sectors and prevent recirculation of gases between the two heads.
  • the invention therefore relates to an annular combustion chamber comprising two concentric heads offset radially one by relative to each other and delimited in the back of the room by a ring gas separator, one of the heads, called the pilot head, operating at idle and full throttle, and the other head, called the take-off head, operating at full gas speed, said separator ring comprising a plurality of elementary sectors disposed circumferentially at a certain distance from each other and fixed on sheets from the bottom of chamber, each sector being shaped into an elongated hollow body, cooled by air circulation from upstream from the bottom of chamber, entering said sector and escaping in both heads through the walls of said sector by a plurality of orifices.
  • This combustion chamber is characterized by the fact that said areas are thermally protected by two sets of tiles covering respectively the upper and lower walls of said sectors, the tiles of the said series being arranged astride two adjacent and remote areas of said walls to allow air cooling circulate in the space thus created, orifices being formed in said tiles to allow the escape of air from cooling in both heads.
  • the drawing shows a combustion chamber 1 of a combustion with two gas turbine heads, delimited by a wall external annular and an internal annular wall, symmetrical of revolution around a common axis, as well as through a chamber bottom 2 connecting the downstream ends of the two annular walls and partially mounted on figure 1.
  • the bottom of chamber 2 is equipped with two groups of injectors fuel distributed over concentric annular rings, different diameters.
  • the injectors of the external group pass through holes 3 of axis Y1 formed in the chamber bottom 2 and cooperate for the fueling of the fuel with air passages passing through the bottom 2 and the walls of enclosure 1.
  • These fuel injectors closest to the wall are intended to operate, being alone in service, at idling speed, and constitute fuel injectors for the pilot head.
  • Internal group injectors also pass through holes 4 Y2 axis formed in the bottom of chamber 2 and are intended for operate at full throttle or takeoff on an equipped aircraft of said gas turbine.
  • a gas separator assembly 10 of generally annular shape, fixed on the bottom of chamber 2, is interposed between the two groups injectors. This separator assembly 10 constitutes a projection the interior of the combustion chamber 1 relative to the chamber bottom 2.
  • the separator assembly 10 gas is constituted by a plurality of elementary hollow sectors 11, of elongated shape, which are arranged circumferentially at a certain distance x from each other and which are each fixed on sheets 12, 13 of the chamber bottom 2 by fixing means 14 distinct from those from other sectors.
  • the sheets 12 and 13 of the chamber bottom 2 are put in forms so as to form, on the side of the combustion chamber 1, a annular groove 15 of inverted U-section of 90 °, and in the bottom of which is engaged the upstream part 16 of each elementary sector 11.
  • Each elementary sector 11 has, in addition to the part upstream 16, of inverted U section, which engages in the bottom of the groove 15 of the chamber bottom 2, an upper wall 17 and a wall lower 18 which are connected at their downstream ends 19, so as to form a corner in the combustion chamber 1, and the ends of which respective upstream 20 and 21 are connected to the wings of the upstream part 16, by connecting walls 22 and 23 which form recesses in such a way that the upstream parts of the walls upper 17 and lower 18 are separated from the sheets 12 respectively and 13 and delimit with the latter annular spaces 24, 25.
  • the upper wall 17 includes in the annular space 24 a external rib 26 parallel to the connecting wall 22 and which forms with the connection wall 22 and the sheet 12 a groove 27.
  • the bottom wall 18 has in the annular space 25 an external rib 28 parallel to the connecting wall 23 and which defines with the latter and the sheet 13 a groove 29.
  • the downstream end 19 for connection of the upper wall 17 and of the bottom wall 18 also has an open groove 30 in the opposite direction to the chamber bottom 2.
  • Two side walls 31, 32 close the ends of each elementary sector 11.
  • the upstream part 16 of each elementary sector 11 and the sheets 12 and 13 of the chamber bottom 2 have corresponding holes 33 for the removal of cooling air upstream from the bottom of chamber 1, this cooling air circulating inside the sector 11 and discharging through a plurality of orifices 34 formed in the walls upper 17 and lower 18 to the combustion chamber 1.
  • the upper walls 17 of the elementary sectors 11 are thermally protected by a first series of tiles 40 arranged each straddling two adjacent tiles 11a, 11b as is visible in Figure 2.
  • the lower walls 18 of the sectors elementary 11 are covered by a second series of tiles 41 each arranged astride two adjacent tiles 11a, 11b.
  • the tiles 40 and 41 each have at their downstream end a hook respectively 42, 43 directed towards the chamber bottom.
  • the hooks 42, 43 of two tiles 40, 41 straddling the same sectors 11a, 11b are intended to accommodate with play, being arranged one on the other in the grooves 30 formed at the downstream ends of these two sectors 11a, 11b.
  • the tiles 40 and 41 also have at their upstream ends ribs 44, 45 arranged on their internal faces and which are intended to be fitted respectively in grooves 27 and 29 provided at the bottom of the external annular grooves 24 and internal annular 25.
  • the heights of the ribs 26 and 44, 28 and 45, and the thicknesses of the walls of tiles 40 and 41 are calculated in such a way that the upstream ends of tiles 40 and 41 are sandwiched between the sheets 12, 13 and the elementary sectors 11.
  • the internal faces of the tiles 40, 41 are maintained spaced from the upper 17 and lower 18 walls by a distance substantially equal to the thickness of the outer ribs 26, 28 for allow the cooling air which escapes through the orifices 34 to circulate in the spaces 46, 47 formed between the tiles 40, 41 and the walls 17, 18 of the elementary sectors 11.
  • This cooling air then escapes through orifices 48, 49 formed in the tiles 40, 41 as well as by a multi-perforation 50 made in the thickness of the tiles 40, 41.
  • the spaces 46, 47 are closed in the circumferential direction by tile returns 51, 52 which are supported on the external faces of the upper 17 and lower 18 walls of adjacent sectors 11a, 11b.
  • Zirconate is deposited on the tiles 40, 41 so to create a thermal barrier.
  • the upstream part of the assembly thus produced is embedded in the groove 15 of the chamber bottom 2, formed by the sheets 12 and 13 and therein fixed by the fixing means 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. , Ringförmige Brennkammer mit zwei konzentrischen Köpfen, die radial gegeneinander versetzt sind und im Boden der Kammer (2) durch einen Gas-Trennring (10) begrenzt sind, wobei einer der Köpfe, Pilotkopf genannt, in verlangsamten und Vollgas-Bereichen arbeitet und der andere Kopf, Ablösekopf genannt, in Vollgas-Bereichen arbeitet, wobei der Trennring (10) mehrere Elementarsektoren (11) aufweist, die in Umfangsrichtung mit bestimmtem Abstand (x) gegeneinander angeordnet sind und an Blechen (12, 13) des Kammerbodens (2) befestigt sind, wobei jeder Sektor (11) als ein länglicher hohler Körper ausgebildet ist, der durch Umwälzung von Luft gekühlt ist, die von stromaufwärts des Kammerbodens (2) kommt, in den Sektor eintritt und in den beiden Köpfen über Wände (17, 18) des Sektors über mehrere Öffnungen (34) austritt,
    dadurch gekennzeichnet, dass die Sektoren (11) thermisch durch zwei Folgen von Belägen (40, 41) geschützt sind, die die oberen (17) bzw. die unteren (18) Wände der Platten bedecken, wobei die Beläge (40, 41) der Folgen auf zwei benachbarten Sektoren (11a, 11b) aufsitzend ausgebildet sind, mit Abstand zu den Wänden (17, 18), damit Kühlluft in dem so gebildeten Raum (46, 47) zirkulieren kann, wobei Öffnungen (48, 49, 50), in den Belägen (40, 41) ausgebildet sind, um das Entweichen der Kühlluft in den beiden Köpfen zu ermöglichen.
  2. Brennkammer nach Anspruch 1,
    dadurch gekennzeichnet, dass jeder Belag (40, 41) an seinem stromabseitigen Ende einen Haken (42, 43) und an seinem stromaufseitigen Ende eine innere Nut (44, 45) aufweist, dass die Sektoren (11) an ihren stromabseitigen Enden eine Fuge (30) aufweisen, in denen die Haken (42, 43) der Beläge (40, 41) aufgenommen sind und nahe den stromaufseitigen Enden ihrer oberen (17) und unteren (18) Wände äußere Nuten (26, 28) aufweisen, die mit den Blechen (12, 13) des Kammerbodens (2) Fugen (27, 28) begrenzen, in denen die inneren Nuten (44, 45) der Beläge (40, 41) aufgenommen sind.
  3. Brennkammer nach Anspruch 2,
    dadurch gekennzeichnet, dass die stromaufseitigen Enden der Beläge (40, 41) zwischen den Wänden (17, 18) der Sektoren und den Blechen (12, 13) des Kammerbodens (2) angeordnet sind, wobei letztere entsprechend konform ausgebildet sind.
  4. Brennkammer nach einem der Ansprüche 2 oder 3,
    dadurch gekennzeichnet, dass die äußeren Nuten (26, 28) der Sektoren (11) Ausnehmungen aufweisen, in denen Rasten (53, 54) eingreifen, die an den inneren Seiten der Beläge (40, 41) ausgebildet sind.
  5. Brennkammer nach einem der Ansprüche 2 bis 4,
    dadurch gekennzeichnet, dass die Haken (42, 43) der Beläge (40) mit Spiel in den Fugen (30) der stromabseitigen Enden der Sektoren (11) aufgenommen sind.
  6. Brennkammer nach einem der Ansprüche 2 bis 5,
    dadurch gekennzeichnet, dass die Beläge (40, 41) mit einer Zirkonatschicht bedeckt sind.
EP99400918A 1998-04-16 1999-04-15 Gasabscheider für eine Brennkammer mit zwei Brennerköpfen Expired - Lifetime EP0950859B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9804704A FR2777634B1 (fr) 1998-04-16 1998-04-16 Separateur pour chambre de combustion a deux tetes
FR9804704 1998-04-16

Publications (2)

Publication Number Publication Date
EP0950859A1 EP0950859A1 (de) 1999-10-20
EP0950859B1 true EP0950859B1 (de) 2004-06-30

Family

ID=9525276

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Application Number Title Priority Date Filing Date
EP99400918A Expired - Lifetime EP0950859B1 (de) 1998-04-16 1999-04-15 Gasabscheider für eine Brennkammer mit zwei Brennerköpfen

Country Status (5)

Country Link
US (1) US6155055A (de)
EP (1) EP0950859B1 (de)
JP (1) JPH11324712A (de)
DE (1) DE69918352T2 (de)
FR (1) FR2777634B1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2856468B1 (fr) * 2003-06-17 2007-11-23 Snecma Moteurs Chambre de combustion annulaire de turbomachine
GB2420614B (en) * 2004-11-30 2009-06-03 Alstom Technology Ltd Tile and exo-skeleton tile structure
DE102007062699A1 (de) * 2007-12-27 2009-07-02 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerauskleidung
US8015817B2 (en) * 2009-06-10 2011-09-13 Siemens Energy, Inc. Cooling structure for gas turbine transition duct
US10101029B2 (en) * 2015-03-30 2018-10-16 United Technologies Corporation Combustor panels and configurations for a gas turbine engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5220795A (en) * 1991-04-16 1993-06-22 General Electric Company Method and apparatus for injecting dilution air
CA2089285C (en) * 1992-03-30 2002-06-25 Stephen Winthrop Falls Segmented centerbody for a double annular combustor
US5285632A (en) * 1993-02-08 1994-02-15 General Electric Company Low NOx combustor
FR2706021B1 (fr) * 1993-06-03 1995-07-07 Snecma Chambre de combustion comprenant un ensemble séparateur de gaz.
US5421158A (en) * 1994-10-21 1995-06-06 General Electric Company Segmented centerbody for a double annular combustor
GB2297830B (en) * 1995-02-07 1998-04-29 Rolls Royce Radially staged annular combustor
US5970716A (en) * 1997-10-02 1999-10-26 General Electric Company Apparatus for retaining centerbody between adjacent domes of multiple annular combustor employing interference and clamping fits

Also Published As

Publication number Publication date
DE69918352T2 (de) 2005-08-25
EP0950859A1 (de) 1999-10-20
FR2777634B1 (fr) 2000-05-19
US6155055A (en) 2000-12-05
FR2777634A1 (fr) 1999-10-22
JPH11324712A (ja) 1999-11-26
DE69918352D1 (de) 2004-08-05

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